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Movement process of spinning microspacecraft


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Movement process of spinning microspacecraft
Liu Yun12Wang Hao2Tao Ruyi2Zhu Delong3
1.The 28th Research Institute of China Electronics Technology Group Corporation,Nanjing 210007,China; 2.School of Energy and Power Engineering,NUST,Nanjing 210094,China; 3.Nanchang Military Academy,Nanchang 330103,China
spacecraftsenvironmental factorsorbital dynamic modelsEuler equationattitude dynamic modelsdualEuler methodorbital parametersattitude parametersair densitygravitational force
To study the movement of a certain spinning microspacecraft running a circle in orbit,primary reference frames are set up to describe the motion states of the spinning microspacecraft.An orbital dynamic model and an attitude dynamic model based on Euler equation are established considering the influences of environmental factors on the flight process of the spinning microspacecraft.The orbital and attitude parameters of the spinning microspacecraft running a circle in orbit are simulated using the dualEuler method.The results indicate that the air density of high altitude orbit is extremely low,and the spinning microspacecraft stabilized by spinning is mainly affected by the gravitational force,solar radiation pressure and atmospheric drag.The motion trajectory of the spinning microspacecraft approximates to a ring;the orbit altitude heightens 4.66 km after the spinning microspacecraft runs a circle;the roll angle and yaw angle fluctuate,the variation is less than ±0.04°;the pitch angle increases gradually over time,the change ranges approximate to 360°.


Liao He,Wang Benli,Cao Zhengli.Predictive unscented Kalman filter for gyroless satellite attitude determination[J].Journal of Nanjing University of Science and Technology,2011,35(5):687-692.
[2]Li Hengnian,Li Jisheng,Huang Yongxuan.A dynamic model compensation orbit determination method for maneuvering satellite[J].Journal of Astronautics,2010,31(10):2269-2275.
Fan Hongshen,Wang Tongquan,Fo Xianchao.A fast and accurate method for spacecraft attitude determination based on a dualfield star sensor[J].Journal of Astronautics,2011,32(6):1276-1280.
Li Yuejun,Yan Chao.Improvement of dualEuler method for full scale Eulerian angles solution of aircraft[J].Journal of Beijing University of Aeronautics and Astronautics,2007,33(5):505-508.
Wang Haifeng,Wang Chengliang.A new solution for singularity of Eular equations[J].Flight Dynamics,2006,24(3):94-96.


Last Update: 2014-06-30